关键词: 超声速进气道;有限体积法;纳维尔－斯托克斯方程;激波

Abstract: A numerical analysis method of three dimensional compressible viscous flow of rectangular supersonic inlet for Hypersonic Ramjet Engine (HRE) was studiedThe major characteristics of this kind of inlet are:ploy shock wave structure,boundary layer shock wave interaction,and second flow existing in the flow field at same timeThe method is based on Jameson’s finite volume schemeIn stead of difference method,an integral scheme is adapted to disperse the viscous terms of Navier Stokes equations ensure the conservation of the schemeVarying coefficient implicit residual smoothing technique was studied to accelerate convergence The specified initial flow field and boundary condition for the supersonic convergence path was discussed

Key words: Supersonic inlet;Finite volume method;Navier Stokes equation;Shock wave